Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Bergey BW-3 (smoothed) (bw3-il) Reynolds number: 500,000 Max Cl/Cd: 88.57 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bw3-il-500000.txt Download as CSV file: xf-bw3-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Bergey BW-3 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3896 0.11200 0.10955 -0.0148 1.0000 0.0236
-8.500 -0.3921 0.10972 0.10730 -0.0161 1.0000 0.0237
-8.250 -0.3927 0.10648 0.10410 -0.0161 1.0000 0.0239
-8.000 -0.3827 0.10298 0.10060 -0.0150 1.0000 0.0241
-7.750 -0.3793 0.10068 0.09832 -0.0142 1.0000 0.0243
-7.500 -0.3775 0.09861 0.09628 -0.0133 1.0000 0.0246
-7.250 -0.3735 0.09639 0.09409 -0.0129 1.0000 0.0250
-7.000 -0.3669 0.09378 0.09151 -0.0136 1.0000 0.0253
-6.750 -0.3600 0.09120 0.08896 -0.0144 1.0000 0.0260
-6.500 -0.3537 0.08860 0.08640 -0.0153 1.0000 0.0270
-6.250 -0.3187 0.08343 0.08120 -0.0296 0.9978 0.0286
-6.000 -0.2895 0.07777 0.07551 -0.0369 0.9958 0.0289
-5.750 -0.2683 0.07474 0.07248 -0.0381 0.9936 0.0294
-5.500 -0.2394 0.07182 0.06955 -0.0424 0.9908 0.0302
-5.250 -0.2056 0.06825 0.06595 -0.0488 0.9876 0.0314
-5.000 -0.1427 0.06193 0.05950 -0.0668 0.9814 0.0343
-4.750 -0.1249 0.05728 0.05484 -0.0691 0.9611 0.0348
-4.500 -0.1042 0.05509 0.05265 -0.0694 0.9498 0.0354
-4.250 -0.0719 0.05246 0.04999 -0.0733 0.9434 0.0364
-4.000 -0.0315 0.04910 0.04656 -0.0796 0.9380 0.0387
-3.750 0.0438 0.01349 0.00853 -0.1078 0.9348 0.0342
-3.500 0.0842 0.03291 0.02984 -0.1041 0.9298 0.0352
-3.250 0.1253 0.03168 0.02855 -0.1082 0.9256 0.0363
-3.000 0.1629 0.01048 0.00491 -0.1156 0.9215 0.0422
-2.750 0.2094 0.01006 0.00444 -0.1197 0.9163 0.0464
-2.500 0.2598 0.00977 0.00411 -0.1248 0.9112 0.0520
-2.250 0.3100 0.00975 0.00407 -0.1299 0.9038 0.0587
-2.000 0.3599 0.01021 0.00451 -0.1348 0.8957 0.0651
-1.750 0.3971 0.01064 0.00500 -0.1368 0.8842 0.0687
-1.500 0.4305 0.01112 0.00549 -0.1378 0.8731 0.0723
-1.250 0.4614 0.01108 0.00529 -0.1383 0.8613 0.0773
-1.000 0.4884 0.01144 0.00569 -0.1379 0.8478 0.0795
-0.750 0.5143 0.01161 0.00586 -0.1372 0.8352 0.0822
-0.500 0.5413 0.01163 0.00575 -0.1367 0.8252 0.0866
-0.250 0.5668 0.01131 0.00535 -0.1360 0.8152 0.0902
0.000 0.5928 0.01137 0.00546 -0.1355 0.8058 0.0927
0.250 0.6192 0.01135 0.00538 -0.1349 0.7963 0.0961
0.500 0.6449 0.01114 0.00510 -0.1342 0.7869 0.0988
0.750 0.6714 0.01118 0.00503 -0.1336 0.7771 0.1008
1.000 0.6962 0.01059 0.00437 -0.1327 0.7644 0.1032
1.250 0.7212 0.01041 0.00416 -0.1318 0.7501 0.1048
1.500 0.7460 0.01029 0.00400 -0.1309 0.7340 0.1064
1.750 0.7711 0.01024 0.00392 -0.1300 0.7187 0.1088
2.000 0.7960 0.01015 0.00377 -0.1291 0.7004 0.1103
2.250 0.8208 0.01010 0.00365 -0.1281 0.6809 0.1117
2.500 0.8456 0.01009 0.00357 -0.1272 0.6605 0.1131
2.750 0.8696 0.01015 0.00356 -0.1261 0.6336 0.1143
3.000 0.8930 0.01016 0.00344 -0.1249 0.5971 0.1159
3.250 0.9149 0.01033 0.00345 -0.1235 0.5468 0.1188
3.500 0.9338 0.01081 0.00360 -0.1214 0.4681 0.1206
3.750 0.9489 0.01174 0.00396 -0.1188 0.3520 0.1223
4.000 0.9586 0.01332 0.00459 -0.1154 0.1699 0.1239
4.250 0.9729 0.01456 0.00529 -0.1128 0.0652 0.1253
4.500 0.9964 0.01493 0.00567 -0.1118 0.0567 0.1273
4.750 1.0208 0.01525 0.00600 -0.1110 0.0519 0.1298
5.000 1.0433 0.01578 0.00660 -0.1099 0.0473 0.1333
5.250 1.0677 0.01608 0.00697 -0.1091 0.0453 0.1378
5.500 1.0909 0.01649 0.00742 -0.1081 0.0430 0.1415
5.750 1.1143 0.01693 0.00792 -0.1073 0.0409 0.1465
6.000 1.1309 0.01799 0.00905 -0.1050 0.0381 0.1521
6.250 1.1551 0.01833 0.00946 -0.1043 0.0370 0.1607
6.500 1.1786 0.01883 0.01007 -0.1035 0.0358 0.1880
6.750 1.3161 0.02015 0.01255 -0.1307 0.0319 1.0000
7.000 1.3315 0.02163 0.01404 -0.1284 0.0306 1.0000
7.250 1.3516 0.02254 0.01501 -0.1268 0.0298 1.0000
7.500 1.3729 0.02323 0.01577 -0.1255 0.0291 1.0000
7.750 1.3936 0.02403 0.01663 -0.1241 0.0283 1.0000
8.000 1.4139 0.02501 0.01767 -0.1227 0.0276 1.0000
8.250 1.4341 0.02597 0.01867 -0.1213 0.0268 1.0000
8.500 1.4540 0.02672 0.01947 -0.1199 0.0260 1.0000
8.750 1.4731 0.02757 0.02032 -0.1185 0.0252 1.0000
9.000 1.4925 0.03068 0.02351 -0.1175 0.0242 1.0000
9.250 1.5107 0.03134 0.02432 -0.1157 0.0238 1.0000
9.500 1.5288 0.03258 0.02574 -0.1139 0.0233 1.0000
9.750 1.5461 0.03418 0.02752 -0.1122 0.0228 1.0000
10.000 1.5620 0.03592 0.02946 -0.1102 0.0223 1.0000
10.250 1.5764 0.03750 0.03120 -0.1081 0.0216 1.0000
10.500 1.5899 0.03896 0.03280 -0.1060 0.0211 1.0000
10.750 1.6031 0.04005 0.03396 -0.1039 0.0207 1.0000
11.000 1.6151 0.04060 0.03453 -0.1017 0.0202 1.0000
11.250 1.6245 0.04249 0.03655 -0.0992 0.0199 1.0000
11.500 1.6273 0.04604 0.04031 -0.0962 0.0195 1.0000
11.750 1.6173 0.05044 0.04509 -0.0914 0.0192 1.0000
12.000 1.6059 0.05247 0.04737 -0.0857 0.0190 1.0000
12.250 1.5923 0.05523 0.05038 -0.0805 0.0189 1.0000
12.500 1.5744 0.05882 0.05425 -0.0757 0.0189 1.0000
12.750 1.5545 0.06283 0.05853 -0.0718 0.0188 1.0000
13.000 1.5332 0.06729 0.06325 -0.0690 0.0187 1.0000
13.250 1.5085 0.07266 0.06887 -0.0672 0.0187 1.0000
13.500 1.4815 0.07878 0.07524 -0.0666 0.0187 1.0000
13.750 1.4561 0.08513 0.08179 -0.0671 0.0188 1.0000
14.000 1.4282 0.09247 0.08935 -0.0690 0.0188 1.0000
14.250 1.4009 0.10038 0.09744 -0.0721 0.0189 1.0000
14.500 1.3759 0.10865 0.10584 -0.0759 0.0191 1.0000
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Polar data table (+)
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